Abstract

This comparative study is concerned with the advances in nozzle guide vane (NGV) design developments and their influence on endwall film cooling performance by injecting coolant through the purge slot. This experimental study compares the film cooling effectiveness and the aerodynamic effects for different purge slot configurations on both a flat and an axisymmetrically contoured endwall of a NGV. While the flat endwall cascade was equipped with cylindrical vanes, the contoured endwall cascade consisted of modern NGVs, which represent state-of-the-art high-pressure turbine design standards. Geometric variations, e.g., the slot width and injection angle, as well as different blowing ratios were realized. The mainstream flow parameters were set to meet real engine conditions with regard to Reynolds and Mach numbers. Pressure-sensitive paint was used to determine the adiabatic film cooling effectiveness. Five-hole probe measurements were performed to measure the flow field in the vane wake region. For a more profound insight into the origin of the secondary flows, oil dye visualizations were carried out. The results show that the advances in NGV design have a significantly positive influence on the distribution of the coolant. This has to be attributed to lesser disturbance of the coolant propagation by secondary flow for the optimized NGV design, since the design features are intended to suppress the formation of secondary flow. Therefore, it is advisable to take these effects into account when designing the film cooling system of a modern high-pressure turbine.

References

1.
Blair
,
M. F.
,
1974
, “
An Experimental Study of Heat Transfer and Film Cooling on Large-Scale Turbine Endwalls
,”
ASME J. Heat. Transfer-Trans. ASME
,
96
(
4
), pp.
524
529
.
2.
Langston
,
L. S.
,
1980
, “
Crossflows in a Turbine Cascade Passage
,”
J. Eng. Power
,
102
(
4
), pp.
866
874
.
3.
Goldstein
,
R. J.
, and
Spores
,
R. A.
,
1988
, “
Turbulent Transport on the Endwall in the Region Between Adjacent Turbine Blades
,”
ASME J. Heat. Transfer-Trans. ASME
,
110
(
4a
), pp.
862
869
.
4.
Wang
,
H.-P.
,
Olson
,
S. J.
,
Goldstein
,
R. J.
, and
Eckert
,
E. R. G.
,
1995
, “
Flow Visualization in a Linear Turbine Cascade of High Performance Turbine Blades
,”
ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
,
Houston, TX
,
June
, pp.
1
11
.
5.
Simon
,
T. W.
, and
Piggush
,
J. D.
,
2006
, “
Turbine Endwall Aerodynamics and Heat Transfer
,”
J. Propul. Power.
,
22
(
2
), pp.
301
312
.
6.
Thrift
,
A. A.
,
Thole
,
K. A.
, and
Hada
,
S.
,
2011
, “
Effects of an Axisymmetric Contoured Endwall on a Nozzle Guide Vane: Adiabatic Effectiveness Measurements
,”
ASME J. Turbomach.
,
133
(
4
), p.
041007
.
7.
Barigozzi
,
G.
,
Franchini
,
G.
,
Perdichizzi
,
A.
, and
Ravelli
,
S.
,
2009
, “
Contouring Effects on the Adiabatic Effectiveness Distribution Over a Film Cooled End Wall Cascade
,”
8th European Turbomachinery Conference – Euroturbo
,
Graz, Austria
,
March
, vol.
1
, pp.
579
590
.
8.
Cardwell
,
N. D.
,
Sundaram
,
N.
, and
Thole
,
K. A.
,
2006
, “
The Effects of Varying the Combustor-Turbine Gap
,”
ASME Turbo Expo 2006: Power for Land, Sea, and Air, Volume 3: Heat Transfer, Parts A and B)
, pp.
91
102
, Paper No. GT2006-90089.
9.
Thrift
,
A. A.
,
Thole
,
K. A.
, and
Hada
,
S.
,
2012
, “
Effects of Orientation and Position of the Combustor-Turbine Interface on the Cooling of a Vane Endwall
,”
ASME J. Turbomach.
,
134
(
6
), p.
061019
.
10.
Müller
,
G.
,
Landfester
,
C.
,
Böhle
,
M.
, and
Krewinkel
,
R.
,
2020
, “
Turbine Vane Endwall Film Cooling Effectiveness of Different Purge Slot Configurations in a Linear Cascade
,”
ASME J. Turbomach.
,
142
(
3
), p.
031008
.
11.
Landfester
,
C.
,
Müller
,
G.
,
Böhle
,
M.
, and
Domnick
,
C.
,
2021
, “
Endwall Film Cooling Effectiveness for Different Purge Slot Configurations in a Contoured Endwall Nozzle Guide Vane Stage
,”
14th European Turbomachinery Conference
,
Gdansk, Poland
,
April
, pp.
1
16
.
12.
Franze
,
R.
,
Böhle
,
M.
,
Krewinkel
,
R.
, and
Wiedermann
,
A.
,
2015
, “
A New Hot Gas Test Stand for Gas Turbine Cooling Investigations
,” International Gas Turbine Conference (IGTC), Paper No. IGTC-2015-72.
13.
Liu
,
T.
, and
Sullivan
,
J. P.
,
2005
,
Pressure and Temperature Sensitive Paints
,
Springer-Verlag
,
Berlin, Germany
.
14.
Charbonnier
,
D.
,
Ott
,
P.
,
Jonsson
,
J.
,
Cottier
,
F.
, and
Köbke
,
T.
,
2009
, “
Experimental and Numerical Study of the Thermal Performance of a Film Cooled Turbine Platform
,”
ASME Turbo Expo 2009: Power for Land, Sea, and Air, Volume 3: Heat Transfer, Parts A and B
, pp.
1027
1038
, Paper No. GT2009-60306.
15.
Landfester
,
C.
,
Müller
,
G.
,
Böhle
,
M.
, and
Krewinkel
,
R.
,
2019
, “
Aerodynamic Effects of Turbine Vane End Wall Film Cooling for Different Purge Slot Configurations in a Linear Cascade
,” International Gas Turbine Conference (IGTC), Paper No. IGTC-201-60.
16.
Natsui
,
G.
,
Little
,
Z.
,
Kapat
,
J. S.
,
Dees
,
J. E.
, and
Laskowski
,
G.
,
2016
, “
A Detailed Uncertainty Analysis of Adiabatic Film Cooling Effectiveness Measurements Using Pressure-Sensitive Paint
,”
ASME J. Turbomach.
,
138
(
8
), p.
081007
.
17.
Kline
,
S. J.
, and
McClintock
,
F. A.
,
1953
, “
Describing Uncertainties in a Single Sample Experiment
,”
Mech. Eng. (Am. Soc. Mech. Eng.)
,
75
(
1
), pp.
3
8
.
18.
Takeishi
,
K.
,
Matsuura
,
M.
,
Aoki
,
S.
, and
Sato
,
T.
,
1990
, “
An Experimental Study of Heat Transfer and Film Cooling on Low Aspect Ratio Turbine Nozzles
,”
ASME J. Turbomach.
,
112
(
3
), pp.
488
496
.
19.
Kopper
,
F. C.
,
Milano
,
R.
,
Davis
,
R. L.
,
Dring
,
R. P.
, and
Stoeffler
,
R. C.
,
1984
, “
Energy Efficient Engine Component Development and Integration Program: High-Pressure Turbine Supersonic Cascade
,”
NASA, Technology Report, Report No. NASA-CR-165567
.
You do not currently have access to this content.